81 FR 58823 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 166 (August 26, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 166 (August 26, 2016)
| Page Range | 58823-58826 | |
| FR Document | 2016-20381 |
[Federal Register Volume 81, Number 166 (Friday, August 26, 2016)] [Rules and Regulations] [Pages 58823-58826] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-20381] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-3696; Directorate Identifier 2015-NM-113-AD; Amendment 39-18625; AD 2016-17-12] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A318 and A319 series airplanes, Model A320-211, -212, - 214, -231, -232, and -233 airplanes, and Model A321 series airplanes. This AD was prompted by a report of a partial loss of the no-back brake (NBB) efficiency during endurance qualification tests on the trimmable horizontal stabilizer actuator (THSA). This AD requires inspecting certain THSAs to determine the number of total flight cycles the THSA has accumulated, and replacing the THSA if necessary. We are issuing this AD to prevent premature wear of the carbon friction disks on the NBB of the THSA, which could lead to reduced braking efficiency in certain load conditions, and, in conjunction with the inability of the power gear train to keep the ball screw in its last commanded position, could result in uncommanded movements of the trimmable horizontal stabilizer and loss of control of the airplane. DATES: This AD is effective September 30, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 30, 2016. ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 3696. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 3696; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800-647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. [[Page 58824]] FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A318 and A319 series airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321 series airplanes. The NPRM published in the Federal Register on February 17, 2016 (81 FR 8023) (``the NPRM''). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0080, dated May 7, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A318 and A319 series airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321 series airplanes. The MCAI states: During endurance qualification tests on A380 Trimmable Horizontal Stabilizer Actuator (THSA), a partial loss of the no-back brake (NBB) efficiency was experienced. Investigation results concluded that this particular malfunction was due to an ageing/ endurance issue of the surfaces of the NBB carbon friction disks, leading to a partial loss of braking efficiency in some specific aerodynamic load conditions. Due to design similarity on A320 family fleet, the same tests were initiated by the THSA manufacturer on certain SA [single-aisle] type THSA, sampled from the field. Subject tests confirmed that THSA Part Number (P/N) 47145 series, as installed on A320 family aeroplanes, are also affected by this partial loss of NBB efficiency. This condition, if not detected and corrected, and in conjunction with the power gear train not able to keep the ball screw in its last commanded position, could lead to an uncommanded movement of the THS, possibly resulting in loss of control of the aeroplane. For the reasons described above, this [EASA] AD requires [inspecting certain THSAs to determine the number of total flight cycles the THSA has accumulated and replacing THSAs having certain total flight cycles] . . . . You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 3696. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Refer to the Latest Service Information Airbus requested that we refer to the latest service information: Airbus Service Bulletin A320-27-1242, Revision 01, dated February 4, 2016 (we referred to Airbus Service Bulletin A320-27-1242, dated February 9, 2015, as the appropriate source of service information for accomplishing the replacement specified in the NPRM). Airbus also requested that we provide credit for previous actions done per Airbus Service Bulletin A320-27-1242, dated February 9, 2015. We agree with the request to refer to the latest service information. Airbus Service Bulletin A320-27-1242, Revision 01, dated February 4, 2016, includes updated information and specifies that no additional work is necessary for airplanes modified by the previous issue. We have revised paragraphs (h)(1) and (h)(2) of this AD to refer to Airbus Service Bulletin A320-27-1242, Revision 01, dated February 4, 2016. We have also added new paragraph (k) to this AD (and redesignated subsequent paragraphs accordingly) to provide credit for actions done as specified in Airbus Service Bulletin A320-27-1242, dated February 9, 2015. Request To Extend the Compliance Times United Airlines (UAL) requested that we extend the compliance times proposed in the NPRM. UAL stated that U.S. operators receive less time to prepare and plan compared to their counterparts in Europe who follow EASA AD 2015-0080, dated May 7, 2015. UAL noted that the large amount of THSAs that need to be replaced will cause cancellations, spare shortages, and interruptions to its operation. UAL recommended a later compliance time than proposed in paragraph (g)(2) of the proposed AD. We disagree with the request to extend the compliance time. UAL did not provide data to substantiate that an extension to the compliance time will provide an acceptable level of safety. We determine AD compliance times primarily on our assessment of the safety risk. Some safety issues are more time-sensitive than others, so we consider the overall risk to the fleet, including the severity of the failure and the likelihood of the failure's occurrence. We and our colleagues in the foreign civil airworthiness authorities (in this case, EASA) work closely with manufacturers to ensure that all appropriate actions are taken at appropriate times to mitigate risks to the fleet and address identified unsafe conditions. In addition, U.S. operators have the same opportunity as their European counterparts to prepare and plan by reviewing and providing comments to EASA's proposed airworthiness directives (PADs). An EASA PAD is a rulemaking document similar to the FAA's NPRM. In most cases, the FAA follows the intent of the AD issued by the state of design; therefore, we encourage U.S. operators to provide feedback to EASA PADs, which are accessible at the following link: http://ad.easa.europa.eu. For this AD, we determined that accomplishing the replacements before specific dates, as stated in the MCAI, are necessary in order to address the identified unsafe condition in a timely manner. Therefore, we have not changed this AD in this regard. However, under the provisions of paragraph (l)(1) of this AD, we may approve requests for adjustments to the compliance time if data are submitted to substantiate that such an adjustment would provide an acceptable level of safety. Request To Remove Replacement Requirement UAL requested that we remove the replacement requirement specified by paragraph (h)(2) of the proposed AD. UAL stated that the requirements in paragraphs (h)(1) and (h)(2) of the proposed AD are contradictory. UAL noted that operators will not be able to predict the future number of flight cycles. UAL stated, as an example, that a THSA having accumulated 38,000 total flight cycles on the effective date would be out of compliance with paragraph (h)(2) of the proposed AD when the AD becomes effective, since the THSA has exceeded 36,000 total flight cycles. We disagree with the request to remove paragraph (h)(2) of this AD. However, we do find it necessary to clarify the requirements. After accomplishing each inspection required by paragraph (g) of this AD, operators must comply with paragraph (h)(1) of this AD, which mandates the first requirement for THSA replacement after each inspection of the THSAs if any part number 47145-(XXX) is found and the THSA has exceeded the corresponding flight-cycle limits specified in [[Page 58825]] paragraphs (g)(1) through (g)(5) of this AD. Paragraph (h)(2) of this AD establishes the life limit of the THSA as of each date specified in paragraphs (g)(1) through (g)(5) of this AD and mandates replacement before the corresponding flight-cycle limit. The flight-cycle limit varies on each date specified in paragraphs (g)(1) through (g)(5) of this AD. Paragraphs (h)(1) and (h)(2) of this AD are separate requirements that do not conflict. For example, if the THSA has accumulated 38,000 total flight cycles as of the effective date of this AD, then paragraph (h)(1) of this AD does not require replacement immediately (on the effective date of this AD) since the THSA has fewer than 40,000 total flight cycles (which is the flight-cycle limit specified in paragraph (g)(1) of this AD). That THSA would be subject to the compliance time of paragraph (h)(2) of this AD, which requires that, as of the effective date of this AD, the THSA must be replaced before exceeding 40,000 total flight cycles until the next inspection is done before December 31, 2016. The new flight- cycle limit as of that date is 36,000 total flight cycles (which is the flight-cycle limit specified in paragraph (g)(2) of this AD). Each U.S. operator has unique fleet utilization data that can assist in predicting the number of flight cycles accumulated on the THSA and therefore can estimate when a THSA must be replaced. However, under the provisions of paragraph (l)(1) of this AD, we may approve requests for adjustments to the compliance time for replacing the THSA if data are submitted to substantiate that such an adjustment would provide an acceptable level of safety. We have not changed this AD in this regard. Change to Paragraph (j) of This AD We made minor changes to the language in paragraph (j) of this AD to clarify the parts installation limitation. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A320-27-1242, Revision 01, dated February 4, 2016. The service information describes procedures for replacing the THSA with a serviceable THSA. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 959 airplanes of U.S. registry. We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $81,515, or $85 per product. In addition, we estimate that any necessary follow-on actions would take about 21 work-hours and require parts costing $26,500, for a cost of $28,285 per product. We have no way of determining the number of aircraft that might need this action. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2016-17-12 Airbus: Amendment 39-18625; Docket No. FAA-2016-3696; Directorate Identifier 2015-NM-113-AD. (a) Effective Date This AD is effective September 30, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Airbus airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, all manufacturer serial numbers. (1) Model A318-111, -112, -121, and -122 airplanes. (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes. (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Reason This AD was prompted by a report of a partial loss of the no- back brake (NBB) efficiency during endurance qualification tests on the trimmable horizontal stabilizer [[Page 58826]] actuator (THSA). We are issuing this AD to prevent premature wear of the carbon friction disks on the NBB of the THSA, which could lead to reduced braking efficiency in certain load conditions, and, in conjunction with the inability of the power gear train to keep the ball screw in its last commanded position, could result in uncommanded movements of the trimmable horizontal stabilizer and loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection To Determine THSA Part Number and Accumulated Total Flight Cycles No later than each date specified in paragraphs (g)(1) through (g)(5) of this AD: Inspect the THSA to determine if it has a part number (P/N) 47145-(XXX), and, if any THSA P/N 47145-(XXX) is found, determine the total number of flight cycles accumulated since the THSA's first installation on an airplane, or since the most recent NBB replacement, whichever is later. A review of airplane delivery or maintenance records is acceptable in lieu of this inspection if the part number of the THSA can be conclusively determined from that review. In case maintenance records concerning the most recent NBB disk replacement are unavailable or incomplete, the total flight cycles accumulated since first installation of the THSA on an airplane apply. (1) As of the effective date of this AD: The THSA flight-cycle limit (since first installation on an airplane, or since the most recent NBB replacement, whichever is later) is 40,000 total flight cycles. (2) As of December 31, 2016: The THSA flight-cycle limit (since first installation on an airplane, or since the most recent NBB replacement, whichever is later) is 36,000 total flight cycles. (3) As of December 31, 2017: The THSA flight-cycle limit (since first installation on an airplane, or since the most recent NBB replacement, whichever is later) is 33,600 total flight cycles. (4) As of December 31, 2018: The THSA flight-cycle limit (since first installation on an airplane, or since the most recent NBB replacement, whichever is later) is 31,600 total flight cycles. (5) As of December 31, 2019: The THSA flight-cycle limit (since first installation on an airplane, or since the most recent NBB replacement, whichever is later) is 30,000 total flight cycles. (h) Replacements For airplanes with any THSA P/N 47145-(XXX): Do the replacements required by paragraphs (h)(1) and (h)(2) of this AD. (1) No later than each date specified in paragraphs (g)(1) through (g)(5) of this AD, replace all THSA that have reached or exceeded on each date the corresponding number of flight cycles specified in paragraphs (g)(1) through (g)(5) of this AD. Do the replacement in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1242, Revision 01, dated February 4, 2016. Affected THSAs must be replaced with serviceable THSAs. (2) As of each date specified in paragraphs (g)(1) through (g)(5) of this AD, and before exceeding the flight cycle limit corresponding to each date, as applicable: Replace each THSA with a serviceable THSA, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1242, Revision 01, dated February 4, 2016. (i) Definition of Serviceable THSA For the purposes of this AD: A serviceable THSA is a THSA that has not exceeded the applicable flight-cycle limits, as specified paragraphs (g)(1) through (g)(5) of this AD, since first installation of the THSA on an airplane or since last NBB replacement, whichever is later. Note 1 to paragraph (i) of this AD: Guidance for NBB disc replacement can be found in UTC Aerospace Systems Service Bulletin 47145-27-17, Revision 1, dated July 21, 2015. (j) Parts Installation Limitation As of each date specified in paragraphs (g)(1) through (g)(5) of this AD, as applicable, only installation of a serviceable THSA P/N 47145-(XXX) is allowed on an airplane. (k) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-27-1242, dated February 9, 2015. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (m) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0080, dated May 7, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-3696. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320-27-1242, Revision 01, dated February 4, 2016. (ii) Reserved. (3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on August 18, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-20381 Filed 8-25-16; 8:45 am] BILLING CODE 4910-13-P
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pylon wiring bracket. We are issuing this AD (i) Related Information airplanes, Model A320–211, –212, –214,
to detect and correct cracking in the engine For more information about this AD, –231, –232, and –233 airplanes, and
pylon wiring bracket. Such cracking could contact Fnu Winarto, Aerospace Engineer, Model A321 series airplanes. This AD
result in damage to adjacent power feeders, Systems and Equipment Branch, ANM–130S, was prompted by a report of a partial
subsequent electrical arcing in a flammable FAA, Seattle ACO, 1601 Lind Avenue SW., loss of the no-back brake (NBB)
leakage zone, and consequent uncontrollable Renton, WA 98057–3356; phone: 425–917– efficiency during endurance
fire. 6659; fax: 425–917–6590; email: qualification tests on the trimmable
(f) Compliance fnu.winarto@faa.gov.
horizontal stabilizer actuator (THSA).
Comply with this AD within the (j) Material Incorporated by Reference This AD requires inspecting certain
compliance times specified, unless already (1) The Director of the Federal Register THSAs to determine the number of total
done. approved the incorporation by reference flight cycles the THSA has accumulated,
(IBR) of the service information listed in this and replacing the THSA if necessary.
(g) One-Time Inspection and Corrective paragraph under 5 U.S.C. 552(a) and 1 CFR
Actions We are issuing this AD to prevent
part 51. premature wear of the carbon friction
Within 88 months after the effective date (2) You must use this service information disks on the NBB of the THSA, which
of this AD: Do a one-time general visual as applicable to do the actions required by
inspection of the engine pylon wiring bracket this AD, unless the AD specifies otherwise.
could lead to reduced braking efficiency
on the left wing for the presence of an (i) Boeing Alert Service Bulletin B787– in certain load conditions, and, in
existing corner relief fillet, in accordance 81205–SB570012–00, Issue 001, dated March conjunction with the inability of the
with Part 1 of the Accomplishment 14, 2013. power gear train to keep the ball screw
Instructions of Boeing Alert Service Bulletin (ii) Reserved. in its last commanded position, could
B787–81205–SB570012–00, Issue 001, dated (3) For service information identified in result in uncommanded movements of
March 14, 2013. Within 88 months after the this AD, contact Boeing Commercial the trimmable horizontal stabilizer and
effective date of this AD, do all applicable Airplanes, Attention: Data & Services loss of control of the airplane.
corrective actions specified in paragraph Management, P.O. Box 3707, MC 2H–65,
(g)(1) or (g)(2) of this AD. Seattle, WA 98124–2207; telephone 206– DATES: This AD is effective September
(1) For airplanes on which the engine 544–5000, extension 1; fax 206–766–5680; 30, 2016.
pylon wiring bracket has a corner relief fillet, Internet https://www.myboeingfleet.com. The Director of the Federal Register
(4) You may view this referenced service
re-identify the part number of the engine approved the incorporation by reference
pylon wiring bracket, in accordance with Part information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, of a certain publication listed in this AD
2 of the Accomplishment Instructions of as of September 30, 2016.
WA. For information on the availability of
Boeing Alert Service Bulletin B787–81205–
this material at the FAA, call 425–227–1221. ADDRESSES: For service information
SB570012–00, Issue 001, dated March 14,
(5) You may view this service information identified in this final rule, contact
2013. that is incorporated by reference at the
(2) For airplanes on which the engine National Archives and Records
Airbus, Airworthiness Office—EIAS, 1
pylon wiring bracket does not have a corner Administration (NARA). For information on Rond Point Maurice Bellonte, 31707
relief fillet, replace the engine pylon wiring the availability of this material at NARA, call Blagnac Cedex, France; telephone +33 5
bracket with a new bracket, in accordance 202–741–6030, or go to: http:// 61 93 36 96; fax +33 5 61 93 44 51; email
with Part 3 of the Accomplishment www.archives.gov/federal-register/cfr/ibr- account.airworth-eas@airbus.com;
Instructions of Boeing Alert Service Bulletin locations.html. Internet http://www.airbus.com. You
B787–81205–SB570012–00, Issue 001, dated may view this referenced service
March 14, 2013. Issued in Renton, Washington, on August
16, 2016. information at the FAA, Transport
(h) Alternative Methods of Compliance Dorr M. Anderson, Airplane Directorate, 1601 Lind Avenue
(AMOCs)
Acting Manager, Transport Airplane SW., Renton, WA. For information on
(1) The Manager, Seattle Aircraft Directorate, Aircraft Certification Service. the availability of this material at the
Certification Office (ACO), FAA, has the [FR Doc. 2016–20374 Filed 8–25–16; 8:45 am] FAA, call 425–227–1221. It is also
authority to approve AMOCs for this AD, if BILLING CODE 4910–13–P
available on the Internet at http://
requested using the procedures found in 14 www.regulations.gov by searching for
CFR 39.19. In accordance with 14 CFR 39.19, and locating Docket No. FAA–2016–
send your request to your principal inspector 3696.
DEPARTMENT OF TRANSPORTATION
or local Flight Standards District Office, as
appropriate. If sending information directly Examining the AD Docket
Federal Aviation Administration
to the manager of the ACO, send it to the
attention of the person identified in
You may examine the AD docket on
paragraph (i) of this AD. Information may be
14 CFR Part 39 the Internet at http://
emailed to: 9-ANM-Seattle-ACO-AMOC- [Docket No. FAA–2016–3696; Directorate
www.regulations.gov by searching for
Requests@faa.gov. Identifier 2015–NM–113–AD; Amendment and locating Docket No. FAA–2016–
(2) Before using any approved AMOC, 39–18625; AD 2016–17–12] 3696; or in person at the Docket
notify your appropriate principal inspector, Management Facility between 9 a.m.
or lacking a principal inspector, the manager RIN 2120–AA64 and 5 p.m., Monday through Friday,
of the local flight standards district office/ except Federal holidays. The AD docket
certificate holding district office. Airworthiness Directives; Airbus
contains this AD, the regulatory
(3) An AMOC that provides an acceptable Airplanes
evaluation, any comments received, and
level of safety may be used for any repair other information. The street address for
AGENCY: Federal Aviation
required by this AD if it is approved by the
Administration (FAA), Department of the Docket Office (telephone 800–647–
ehiers on DSK5VPTVN1PROD with RULES
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has Transportation (DOT). 5527) is Docket Management Facility,
been authorized by the Manager, Seattle ACTION: Final rule. U.S. Department of Transportation,
ACO, to make those findings. For a repair Docket Operations, M–30, West
method to be approved, the repair must meet SUMMARY: We are adopting a new Building Ground Floor, Room W12–140,
the certification basis of the airplane, and the airworthiness directive (AD) for all 1200 New Jersey Avenue SE.,
approval must specifically refer to this AD. Airbus Model A318 and A319 series Washington, DC 20590.
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FOR FURTHER INFORMATION CONTACT: Comments the likelihood of the failure’s
Sanjay Ralhan, Aerospace Engineer, We gave the public the opportunity to occurrence.
International Branch, ANM–116, We and our colleagues in the foreign
participate in developing this AD. The
Transport Airplane Directorate, FAA, civil airworthiness authorities (in this
following presents the comments
1601 Lind Avenue SW., Renton, WA case, EASA) work closely with
received on the NPRM and the FAA’s
98057–3356; telephone 425–227–1405; manufacturers to ensure that all
response to each comment.
fax 425–227–1149. appropriate actions are taken at
Request To Refer to the Latest Service appropriate times to mitigate risks to the
SUPPLEMENTARY INFORMATION: fleet and address identified unsafe
Information
Discussion conditions. In addition, U.S. operators
Airbus requested that we refer to the
have the same opportunity as their
latest service information: Airbus
We issued a notice of proposed European counterparts to prepare and
Service Bulletin A320–27–1242,
rulemaking (NPRM) to amend 14 CFR plan by reviewing and providing
Revision 01, dated February 4, 2016 (we
part 39 by adding an AD that would comments to EASA’s proposed
referred to Airbus Service Bulletin
apply to all Airbus Model A318 and airworthiness directives (PADs). An
A320–27–1242, dated February 9, 2015,
A319 series airplanes, Model A320–211, EASA PAD is a rulemaking document
as the appropriate source of service
–212, –214, –231, –232, and –233 similar to the FAA’s NPRM. In most
information for accomplishing the
airplanes, and Model A321 series cases, the FAA follows the intent of the
replacement specified in the NPRM). AD issued by the state of design;
airplanes. The NPRM published in the
Airbus also requested that we provide therefore, we encourage U.S. operators
Federal Register on February 17, 2016
credit for previous actions done per to provide feedback to EASA PADs,
(81 FR 8023) (‘‘the NPRM’’).
Airbus Service Bulletin A320–27–1242, which are accessible at the following
The European Aviation Safety Agency dated February 9, 2015.
(EASA), which is the Technical Agent link: http://ad.easa.europa.eu.
We agree with the request to refer to For this AD, we determined that
for the Member States of the European the latest service information. Airbus accomplishing the replacements before
Union, has issued EASA Airworthiness Service Bulletin A320–27–1242, specific dates, as stated in the MCAI, are
Directive 2015–0080, dated May 7, 2015 Revision 01, dated February 4, 2016, necessary in order to address the
(referred to after this as the Mandatory includes updated information and identified unsafe condition in a timely
Continuing Airworthiness Information, specifies that no additional work is manner. Therefore, we have not
or ‘‘the MCAI’’), to correct an unsafe necessary for airplanes modified by the changed this AD in this regard.
condition for all Airbus Model A318 previous issue. We have revised However, under the provisions of
and A319 series airplanes, Model A320– paragraphs (h)(1) and (h)(2) of this AD paragraph (l)(1) of this AD, we may
211, –212, –214, –231, –232, and –233 to refer to Airbus Service Bulletin approve requests for adjustments to the
airplanes, and Model A321 series A320–27–1242, Revision 01, dated compliance time if data are submitted to
airplanes. The MCAI states: February 4, 2016. We have also added substantiate that such an adjustment
During endurance qualification tests on new paragraph (k) to this AD (and would provide an acceptable level of
A380 Trimmable Horizontal Stabilizer redesignated subsequent paragraphs safety.
Actuator (THSA), a partial loss of the no-back accordingly) to provide credit for
brake (NBB) efficiency was experienced. actions done as specified in Airbus Request To Remove Replacement
Investigation results concluded that this Service Bulletin A320–27–1242, dated Requirement
particular malfunction was due to an ageing/ February 9, 2015. UAL requested that we remove the
endurance issue of the surfaces of the NBB
replacement requirement specified by
carbon friction disks, leading to a partial loss Request To Extend the Compliance
of braking efficiency in some specific paragraph (h)(2) of the proposed AD.
Times
aerodynamic load conditions. UAL stated that the requirements in
Due to design similarity on A320 family United Airlines (UAL) requested that paragraphs (h)(1) and (h)(2) of the
fleet, the same tests were initiated by the we extend the compliance times proposed AD are contradictory. UAL
THSA manufacturer on certain SA [single- proposed in the NPRM. UAL stated that noted that operators will not be able to
aisle] type THSA, sampled from the field. U.S. operators receive less time to predict the future number of flight
Subject tests confirmed that THSA Part prepare and plan compared to their cycles. UAL stated, as an example, that
Number (P/N) 47145 series, as installed on counterparts in Europe who follow a THSA having accumulated 38,000
A320 family aeroplanes, are also affected by EASA AD 2015–0080, dated May 7, total flight cycles on the effective date
this partial loss of NBB efficiency.
2015. UAL noted that the large amount would be out of compliance with
This condition, if not detected and
corrected, and in conjunction with the power of THSAs that need to be replaced will paragraph (h)(2) of the proposed AD
gear train not able to keep the ball screw in cause cancellations, spare shortages, when the AD becomes effective, since
its last commanded position, could lead to an and interruptions to its operation. UAL the THSA has exceeded 36,000 total
uncommanded movement of the THS, recommended a later compliance time flight cycles.
possibly resulting in loss of control of the than proposed in paragraph (g)(2) of the We disagree with the request to
aeroplane. proposed AD. remove paragraph (h)(2) of this AD.
For the reasons described above, this We disagree with the request to However, we do find it necessary to
[EASA] AD requires [inspecting certain extend the compliance time. UAL did clarify the requirements. After
THSAs to determine the number of total
not provide data to substantiate that an accomplishing each inspection required
flight cycles the THSA has accumulated and
replacing THSAs having certain total flight extension to the compliance time will by paragraph (g) of this AD, operators
cycles] . . . . provide an acceptable level of safety. must comply with paragraph (h)(1) of
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We determine AD compliance times this AD, which mandates the first
You may examine the MCAI in the primarily on our assessment of the requirement for THSA replacement after
AD docket on the Internet at http:// safety risk. Some safety issues are more each inspection of the THSAs if any part
www.regulations.gov by searching for time-sensitive than others, so we number 47145–(XXX) is found and the
and locating Docket No. FAA–2016– consider the overall risk to the fleet, THSA has exceeded the corresponding
3696. including the severity of the failure and flight-cycle limits specified in
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![Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations 58825
paragraphs (g)(1) through (g)(5) of this burden on any operator or increase the responsibilities among the various
AD. scope of this AD. levels of government.
Paragraph (h)(2) of this AD establishes For the reasons discussed above, I
the life limit of the THSA as of each date Related Service Information Under
certify that this AD:
specified in paragraphs (g)(1) through 1 CFR Part 51
1. Is not a ‘‘significant regulatory
(g)(5) of this AD and mandates We reviewed Airbus Service Bulletin action’’ under Executive Order 12866;
replacement before the corresponding A320–27–1242, Revision 01, dated 2. Is not a ‘‘significant rule’’ under the
flight-cycle limit. The flight-cycle limit February 4, 2016. The service DOT Regulatory Policies and Procedures
varies on each date specified in information describes procedures for (44 FR 11034, February 26, 1979);
paragraphs (g)(1) through (g)(5) of this replacing the THSA with a serviceable 3. Will not affect intrastate aviation in
AD. Paragraphs (h)(1) and (h)(2) of this THSA. This service information is Alaska; and
AD are separate requirements that do reasonably available because the 4. Will not have a significant
not conflict. interested parties have access to it economic impact, positive or negative,
For example, if the THSA has through their normal course of business on a substantial number of small entities
accumulated 38,000 total flight cycles as or by the means identified in the under the criteria of the Regulatory
of the effective date of this AD, then ADDRESSES section. Flexibility Act.
paragraph (h)(1) of this AD does not
Costs of Compliance List of Subjects in 14 CFR Part 39
require replacement immediately (on
the effective date of this AD) since the We estimate that this AD affects 959 Air transportation, Aircraft, Aviation
THSA has fewer than 40,000 total flight airplanes of U.S. registry. safety, Incorporation by reference,
cycles (which is the flight-cycle limit We also estimate that it would take Safety.
specified in paragraph (g)(1) of this AD). about 1 work-hour per product to
comply with the basic requirements of Adoption of the Amendment
That THSA would be subject to the
compliance time of paragraph (h)(2) of this AD. The average labor rate is $85 Accordingly, under the authority
this AD, which requires that, as of the per work-hour. Based on these figures, delegated to me by the Administrator,
effective date of this AD, the THSA we estimate the cost of this AD on U.S. the FAA amends 14 CFR part 39 as
must be replaced before exceeding operators to be $81,515, or $85 per follows:
40,000 total flight cycles until the next product.
inspection is done before December 31, In addition, we estimate that any PART 39—AIRWORTHINESS
2016. The new flight-cycle limit as of necessary follow-on actions would take DIRECTIVES
that date is 36,000 total flight cycles about 21 work-hours and require parts
costing $26,500, for a cost of $28,285 ■ 1. The authority citation for part 39
(which is the flight-cycle limit specified
per product. We have no way of continues to read as follows:
in paragraph (g)(2) of this AD).
Each U.S. operator has unique fleet determining the number of aircraft that Authority: 49 U.S.C. 106(g), 40113, 44701.
utilization data that can assist in might need this action.
§ 39.13 [Amended]
predicting the number of flight cycles Authority for This Rulemaking
accumulated on the THSA and therefore ■ 2. The FAA amends § 39.13 by adding
can estimate when a THSA must be Title 49 of the United States Code the following new airworthiness
replaced. However, under the specifies the FAA’s authority to issue directive (AD):
provisions of paragraph (l)(1) of this AD, rules on aviation safety. Subtitle I,
2016–17–12 Airbus: Amendment 39–18625;
we may approve requests for section 106, describes the authority of Docket No. FAA–2016–3696; Directorate
adjustments to the compliance time for the FAA Administrator. ‘‘Subtitle VII: Identifier 2015–NM–113–AD.
replacing the THSA if data are Aviation Programs,’’ describes in more
detail the scope of the Agency’s (a) Effective Date
submitted to substantiate that such an
authority. This AD is effective September 30, 2016.
adjustment would provide an acceptable
level of safety. We have not changed We are issuing this rulemaking under (b) Affected ADs
this AD in this regard. the authority described in ‘‘Subtitle VII,
None.
Part A, Subpart III, Section 44701:
Change to Paragraph (j) of This AD General requirements.’’ Under that (c) Applicability
We made minor changes to the section, Congress charges the FAA with This AD applies to Airbus airplanes,
language in paragraph (j) of this AD to promoting safe flight of civil aircraft in certificated in any category, identified in
clarify the parts installation limitation. air commerce by prescribing regulations paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of
for practices, methods, and procedures this AD, all manufacturer serial numbers.
Conclusion the Administrator finds necessary for (1) Model A318–111, –112, –121, and –122
safety in air commerce. This regulation airplanes.
We reviewed the relevant data,
(2) Model A319–111, –112, –113, –114,
considered the comments received, and is within the scope of that authority
–115, –131, –132, and –133 airplanes.
determined that air safety and the because it addresses an unsafe condition (3) Model A320–211, –212, –214, –231,
public interest require adopting this AD that is likely to exist or develop on –232, and –233 airplanes.
with the changes described previously products identified in this rulemaking (4) Model A321–111, –112, –131, –211,
and minor editorial changes. We have action. –212, –213, –231, and –232 airplanes.
determined that these minor changes: Regulatory Findings (d) Subject
• Are consistent with the intent that
was proposed in the NPRM for We determined that this AD will not Air Transport Association (ATA) of
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have federalism implications under America Code 27, Flight Controls.
correcting the unsafe condition; and
• Do not add any additional burden Executive Order 13132. This AD will (e) Reason
upon the public than was already not have a substantial direct effect on This AD was prompted by a report of a
proposed in the NPRM. the States, on the relationship between partial loss of the no-back brake (NBB)
We also determined that these the national government and the States, efficiency during endurance qualification
changes will not increase the economic or on the distribution of power and tests on the trimmable horizontal stabilizer
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![58826 Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations
actuator (THSA). We are issuing this AD to dated February 4, 2016. Affected THSAs (3) Required for Compliance (RC): If any
prevent premature wear of the carbon friction must be replaced with serviceable THSAs. service information contains procedures or
disks on the NBB of the THSA, which could (2) As of each date specified in paragraphs tests that are identified as RC, those
lead to reduced braking efficiency in certain (g)(1) through (g)(5) of this AD, and before procedures and tests must be done to comply
load conditions, and, in conjunction with the exceeding the flight cycle limit with this AD; any procedures or tests that are
inability of the power gear train to keep the corresponding to each date, as applicable: not identified as RC are recommended. Those
ball screw in its last commanded position, Replace each THSA with a serviceable procedures and tests that are not identified
could result in uncommanded movements of THSA, in accordance with the as RC may be deviated from using accepted
the trimmable horizontal stabilizer and loss Accomplishment Instructions of Airbus methods in accordance with the operator’s
of control of the airplane. Service Bulletin A320–27–1242, Revision 01, maintenance or inspection program without
dated February 4, 2016. obtaining approval of an AMOC, provided
(f) Compliance the procedures and tests identified as RC can
(i) Definition of Serviceable THSA be done and the airplane can be put back in
Comply with this AD within the
compliance times specified, unless already For the purposes of this AD: A serviceable an airworthy condition. Any substitutions or
done. THSA is a THSA that has not exceeded the changes to procedures or tests identified as
applicable flight-cycle limits, as specified RC require approval of an AMOC.
(g) Inspection To Determine THSA Part paragraphs (g)(1) through (g)(5) of this AD,
Number and Accumulated Total Flight since first installation of the THSA on an (m) Special Flight Permits
Cycles airplane or since last NBB replacement, Special flight permits, as described in
No later than each date specified in whichever is later. Section 21.197 and Section 21.199 of the
paragraphs (g)(1) through (g)(5) of this AD: Note 1 to paragraph (i) of this AD: Federal Aviation Regulations (14 CFR 21.197
Guidance for NBB disc replacement can be and 21.199), are not allowed.
Inspect the THSA to determine if it has a part
number (P/N) 47145–(XXX), and, if any found in UTC Aerospace Systems Service (n) Related Information
THSA P/N 47145–(XXX) is found, determine Bulletin 47145–27–17, Revision 1, dated July
21, 2015. (1) Refer to Mandatory Continuing
the total number of flight cycles accumulated Airworthiness Information (MCAI) EASA
since the THSA’s first installation on an Airworthiness Directive 2015–0080, dated
(j) Parts Installation Limitation
airplane, or since the most recent NBB May 7, 2015, for related information. This
replacement, whichever is later. A review of As of each date specified in paragraphs
MCAI may be found in the AD docket on the
airplane delivery or maintenance records is (g)(1) through (g)(5) of this AD, as applicable,
Internet at http://www.regulations.gov by
acceptable in lieu of this inspection if the only installation of a serviceable THSA P/N
searching for and locating Docket No. FAA–
part number of the THSA can be conclusively 47145–(XXX) is allowed on an airplane.
2016–3696.
determined from that review. In case (k) Credit for Previous Actions (2) Service information identified in this
maintenance records concerning the most AD that is not incorporated by reference is
recent NBB disk replacement are unavailable This paragraph provides credit for actions
required by paragraph (h) of this AD, if those available at the addresses specified in
or incomplete, the total flight cycles paragraphs (o)(3) and (o)(4) of this AD.
actions were performed before the effective
accumulated since first installation of the
date of this AD using Airbus Service Bulletin (o) Material Incorporated by Reference
THSA on an airplane apply.
A320–27–1242, dated February 9, 2015.
(1) As of the effective date of this AD: The (1) The Director of the Federal Register
THSA flight-cycle limit (since first (l) Other FAA AD Provisions approved the incorporation by reference
installation on an airplane, or since the most The following provisions also apply to this (IBR) of the service information listed in this
recent NBB replacement, whichever is later) AD: paragraph under 5 U.S.C. 552(a) and 1 CFR
is 40,000 total flight cycles. (1) Alternative Methods of Compliance part 51.
(2) As of December 31, 2016: The THSA (AMOCs): The Manager, International (2) You must use this service information
flight-cycle limit (since first installation on Branch, ANM–116, Transport Airplane as applicable to do the actions required by
an airplane, or since the most recent NBB Directorate, FAA, has the authority to this AD, unless this AD specifies otherwise.
replacement, whichever is later) is 36,000 approve AMOCs for this AD, if requested (i) Airbus Service Bulletin A320–27–1242,
total flight cycles. using the procedures found in 14 CFR 39.19. Revision 01, dated February 4, 2016.
(3) As of December 31, 2017: The THSA In accordance with 14 CFR 39.19, send your (ii) Reserved.
flight-cycle limit (since first installation on request to your principal inspector or local (3) For service information identified in
an airplane, or since the most recent NBB Flight Standards District Office, as this AD, contact Airbus, Airworthiness
replacement, whichever is later) is 33,600 appropriate. If sending information directly Office—EIAS, 1 Rond Point Maurice
total flight cycles. to the International Branch, send it to ATTN: Bellonte, 31707 Blagnac Cedex, France;
(4) As of December 31, 2018: The THSA Sanjay Ralhan, Aerospace Engineer, telephone +33 5 61 93 36 96; fax +33 5 61
flight-cycle limit (since first installation on International Branch, ANM–116, Transport 93 44 51; email account.airworth-eas@
an airplane, or since the most recent NBB Airplane Directorate, FAA, 1601 Lind airbus.com; Internet http://www.airbus.com.
replacement, whichever is later) is 31,600 Avenue SW., Renton, WA 98057–3356; (4) You may view this service information
total flight cycles. telephone 425–227–1405; fax 425–227–1149. at the FAA, Transport Airplane Directorate,
(5) As of December 31, 2019: The THSA Information may be emailed to: 9-ANM-116- 1601 Lind Avenue SW., Renton, WA. For
flight-cycle limit (since first installation on AMOC-REQUESTS@faa.gov. Before using information on the availability of this
an airplane, or since the most recent NBB any approved AMOC, notify your appropriate material at the FAA, call 425–227–1221.
replacement, whichever is later) is 30,000 principal inspector, or lacking a principal (5) You may view this service information
total flight cycles. inspector, the manager of the local flight that is incorporated by reference at the
standards district office/certificate holding National Archives and Records
(h) Replacements Administration (NARA). For information on
district office. The AMOC approval letter
For airplanes with any THSA P/N 47145– must specifically reference this AD. the availability of this material at NARA, call
(XXX): Do the replacements required by (2) Contacting the Manufacturer: For any 202–741–6030, or go to: http://
paragraphs (h)(1) and (h)(2) of this AD. requirement in this AD to obtain corrective www.archives.gov/federal-register/cfr/ibr-
(1) No later than each date specified in actions from a manufacturer, the action must locations.html.
paragraphs (g)(1) through (g)(5) of this AD, be accomplished using a method approved Issued in Renton, Washington, on August
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replace all THSA that have reached or by the Manager, International Branch, ANM– 18, 2016.
exceeded on each date the corresponding 116, Transport Airplane Directorate, FAA; or Dorr M. Anderson,
number of flight cycles specified in the European Aviation Safety Agency
Acting Manager, Transport Airplane
paragraphs (g)(1) through (g)(5) of this AD. (EASA); or Airbus’s EASA Design
Directorate, Aircraft Certification Service.
Do the replacement in accordance with the Organization Approval (DOA). If approved by
Accomplishment Instructions of Airbus the DOA, the approval must include the [FR Doc. 2016–20381 Filed 8–25–16; 8:45 am]
Service Bulletin A320–27–1242, Revision 01, DOA-authorized signature. BILLING CODE 4910–13–P
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Document Created: 2016-08-26 10:40:10
Document Modified: 2016-08-26 10:40:10
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective September 30, 2016. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 81 FR 58823 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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